Model Reference Adaptive Control For Aeroengine

Aeroengine is a kind of multi-variable controlled object with strong nonlinearity and coupling, which is usually difficult to be described by precise mathematical models. Even though the mathematical model is built in a stable working state, the structure or parameters of the mathematical model which describes the characteristics of the aeroengine will change accordingly with the changing of the flight condition and working state. It is often difficult to achieve satisfactory performance and index requirements by using traditional feedback con-trol methods or optimal control theory to design the aeroengine's control system. Based on this, this thesis presents a model reference adaptive control method, which depends little on precise mathematical model, for the design of the aeroengine's control system.Firstly, this thesis builds the small deviation dynamic model of a certain type of biaxial aeroengine without afterburner, and obtains the State Space Models of the aeroengine in three stable operating points by pumping power method. Secondly, this thesis designs the model reference adaptive control system for aeroengine based on Popov stability method, aiming at the slow change of model parameters near aeroengine's stable operating points, and gets the adaptive control law which is given by Adaptive Signal Synthetic Control Method. Thirdly, aiming at the condition that near the aeroengine's stable operating points, model parameters are unknown but unchanged with time, this thesis designs aeroengine model reference adap-tive control system based on the Lyapunov stability theory, by choosing Lyapunov function skillfully, in the case of keeping the system stable, the adaptive parameter adjustment law is obtained. Last but not least, this thesis proposes improvement measures to deal with the shak-ing rotating speed problem of the aeroengine model reference adaptive control system as the use of the Lyapunov method.By simulation experiments, the use of two kinds of stability design methods in the aeroengine model reference adaptive control system are verified, and the results prove that the designed control system can realize adaptive state tracking control of aeroengine, and as well meet the performance index requirements for the aeroengine's control system.